Unmanned aerial vehicle with ducted rotors

Abstract

The present disclosure provides a system and device for drones with ducted rotors. In some aspects, drones may comprise one or more systems of ducted rotors. In some embodiments, ducted rotors may increase the durability of the drone, limiting exposure of the rotors to external conditions and objects. In some aspects, a drone with ducted rotors may comprise a control vane or cone that may direct airflow within the drone as a mechanism to control flight path. In some implementations, a drone may comprise expandable landing gear than may allow for controlled landing, even in the event of rotor failure. In some aspects, a drone may comprise rotatable ducted rotors.

What is claimed is: 
     
       1. A drone with ducted rotors comprising:
 a body; 
 a first duct connected to the body; 
 a first rotor system located within the first duct, wherein the first rotor system provides lift and propulsion for flight of the drone; 
 a power source connected; 
 a control mechanism configured to operate flight of the drone, wherein the control mechanism is in logical communication with the power source; 
 a communication mechanism configured to receive instructions for operation of the drone and relay instructions to the control mechanism; 
 a directional control mechanism configured to affect a direction of flight of the drone, wherein the directional control mechanism comprises a cone that controls direction of airflow from the first rotor system, and wherein direction of airflow controls the direction of flight; and 
 a housing connected to the body, wherein the housing contains at least a portion of one or more of the power source, the control mechanism, the communication mechanism, and the directional control mechanism. 
 
     
     
       2. The drone of  claim 1 , wherein the directional control mechanism further comprises a vane that further controls direction of airflow from the first rotor system. 
     
     
       3. The drone of  claim 1 , wherein the duct is located centrally to the body. 
     
     
       4. The drone of  claim 1 , further comprising:
 a second duct connected to the body; and 
 a second rotor system located within the second duct, wherein the first rotor system and the second rotor system provide lift and propulsion for flight of the drone. 
 
     
     
       5. The drone of  claim 4 , wherein the body is located between the first duct and the second duct. 
     
     
       6. The drone of  claim 4 , wherein the drone is configured to operate with one or both the first rotor system and the second rotor system. 
     
     
       7. The drone of  claim 6 , wherein loss of either the first rotor system or the second rotor system causes a shift in orientation of the body. 
     
     
       8. The drone of  claim 4 , wherein the first rotor system and the second rotor system are independently controllable. 
     
     
       9. The drone of  claim 4 , wherein the first rotor system and the second rotor system are controllable as a single system. 
     
     
       10. The drone of  claim 1 , further comprising an expandable landing mechanism configured to slow a descent of the drone. 
     
     
       11. The drone of  claim 10 , wherein the expandable landing mechanism is configured to deploy if the first rotor system fails. 
     
     
       12. The drone of  claim 10 , wherein the body comprises a walled frame, and the expandable landing mechanism comprises a series of expandable panels lining the walled frame. 
     
     
       13. The drone of  claim 10 , wherein the expandable landing mechanism comprises collapsible wings. 
     
     
       14. The drone of  claim 10 , wherein the expandable landing mechanism is configured to rotate on descent when deployed. 
     
     
       15. The drone of  claim 1 , wherein an angle of the first duct is adjustable. 
     
     
       16. The drone of  claim 15 , wherein the angle of the first duct affects the direction of flight, and wherein the directional control mechanism adjusts the angle of the first duct. 
     
     
       17. The drone of  claim 1 , wherein an angle of the first rotor system is adjustable. 
     
     
       18. The drone of  claim 17 , wherein the directional control mechanism adjusts the angle of the first rotor system. 
     
     
       19. The drone of  claim 17 , wherein a first angle of the first rotor system provides primarily lift and a second angle of the first rotor system provides primarily propulsion.